Optimal Three Burn Orbit Transfer

Abstract

This report presents an optimal three burn solution to a class of orbit transfer problems requiring large changes in orbital inclination. A nonlinear programming algorithm was used in conjunction with a simplified trajectory simulation, which used Keplerian orbit transfers and impulsive velocity increments. A number of parametric results were obtained using the simplified simulation. The validity of the simplified simulation was established for specific vehicle configurations with finite burns and oblate earth effects included. The effect of multiple stage rockets has also been treated.

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Document Details

Document Type
Technical Report
Publication Date
Mar 21, 1977
Accession Number
ADA039257

Entities

People

  • J. Betts

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Altitude
  • Apogees
  • Circular Orbits
  • Computer Programming
  • Coordinate Systems
  • Earth Models
  • Equations Of Motion
  • Nonlinear Programming
  • Optimization
  • Orbital Elements
  • Orbital Inclination
  • Orbits
  • Simulations
  • Trajectories
  • Transfer Orbits

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Space Exploration and Orbital Mechanics.
  • Trauma Surgery or Emergency Medicine.

Technology Areas

  • Space
  • Space - Orbital Debris